EP2087208B1 - Turbo engine - Google Patents

Turbo engine Download PDF

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Publication number
EP2087208B1
EP2087208B1 EP07846281A EP07846281A EP2087208B1 EP 2087208 B1 EP2087208 B1 EP 2087208B1 EP 07846281 A EP07846281 A EP 07846281A EP 07846281 A EP07846281 A EP 07846281A EP 2087208 B1 EP2087208 B1 EP 2087208B1
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EP
European Patent Office
Prior art keywords
ring
bellows
rotor
turbo
cavity
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Not-in-force
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EP07846281A
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German (de)
French (fr)
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EP2087208B9 (en
EP2087208A1 (en
Inventor
Alexander Böck
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP2087208B9 publication Critical patent/EP2087208B9/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1.
  • a turbomachine including a stator and a rotor wherein the rotor includes rotor blades and the stator includes a housing and vanes.
  • the rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same.
  • the radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining.
  • the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage. It is after the DE 10 2004 037 955 A1 the radially inner housing wall or the shroud segmented in the circumferential direction, wherein preferably each segment is associated with a separate adjusting device.
  • the adjusting devices are preferably designed as electro-mechanical actuators.
  • the DE 101 17 231 A1 discloses a turbomachine with a stator and a rotor, wherein the gap between radially outer ends of the blades and the radially inner housing wall by means of a pneumatic, so compressed air operated, actuator unit of a rotor gap control module can be adjusted.
  • the pneumatic actuator unit of the disclosed therein rotor gap control module has an actuator chamber, a pressure chamber and the actuator chamber and the pressure chamber connecting valves, which are inflated depending on the prevailing pressure in the actuator chamber sealing elements of the rotor gap control module, so in the sense of a pneumatic active clearance Control to adjust or adjust the gap of the gap between radially outer ends of blades and the outer ring of the housing.
  • the DE 29 22 835 C2 and the US 5,211,534 reveal further turbomachinery with a pneumatic or pneumatic Active Clearance Control.
  • the turbomachine according to DE 29 22 835 C2 via a stator and a rotor, wherein the gap between radially outer ends of the blades and an inner ring or shroud of a housing wall can be adjusted pneumatically.
  • the shroud ring is connected via resilient side walls with a support ring, wherein the shroud, the support ring and the side walls form a bellows-like structure.
  • the gap between radially outer ends of the blades and the shroud can be adjusted.
  • the flexible side walls arched several times.
  • the side walls are after the DE 29 22 835 C2 Accordingly, seen in the axial direction in sections, inwardly into the cavity and partially outwardly curved out of the cavity.
  • the document US-A-5,344,284 protects a pneumatic Active Clearance Control System with a rigid, sheet-like, circumferentially multi-segmented squelch, with each pad segment radially movable via a separate, flexible, rubber-like bellows.
  • the bellows at the upstream and downstream end simply in the cavity of the bellows in curved walls. From the vertex of the curvature to the radially inner end of the bellows wall, a sealing overlap of the bellows wall with a radially outwardly projecting edge of the rigid Anstreifbelags is present. In this area, the bellows wall in the axial direction to the outside is not or only very limited mobility.
  • the structure according to US-A-5344284 is a so-called composite consisting of bellows and shell ring without connection to benochbarten Leitschautelkränzen.
  • the present invention is based on the problem to provide a novel turbomachine with a pneumatic Active Clearance Control.
  • each wall connecting the jacket ring to the support ring is, seen in the axial direction, exclusively inwardly inward arched into the respective cavity.
  • each curved wall is designed in the manner of a toggle lever, wherein the wall sections include an obtuse angle greater than 90 ° and are suitable for receiving pressure forces.
  • Fig. 1 shows a partial cross-section through a stator of a compressor 10 of a turbomachine, wherein the stator comprises a housing 11 and a plurality of stationary vanes 12.
  • the stator-side guide vanes 12 form so-called vane rings which, viewed in the axial direction, are arranged one behind the other.
  • a total of four fixed, stator vane rings 13, 14, 15 and 16 are shown.
  • the compressor 10 comprises an in Fig. 1 Rotor, not shown, wherein the rotor of a plurality of axially arranged behind the other, not shown rotor disks is formed, each rotor disk in the circumferential direction next to each other several, also not shown blades carries.
  • the rotor blades associated, circumferentially juxtaposed blades form so-called blade rings, wherein between each two adjacent vane rings 13 and 14, 14 and 15 and 15 and 16 are each a non-illustrated blade ring is arranged.
  • the housing 11 of the stator of the compressor 10 comprises a radially inner housing wall, wherein the radially inner housing wall in the region of each rotor-side, in Fig. 1 not shown blade ring forms a so-called inner ring or shroud 17 and surrounds the respective blade ring radially on the outside.
  • the housing 11 further comprises a radially outer housing wall 18th
  • each non-illustrated, rotor-side blade ring forms the radially inner housing wall in the region of each non-illustrated, rotor-side blade ring a so-called shroud ring 17 which surrounds the blade ring radially outward.
  • shroud ring 17 which surrounds the blade ring radially outward.
  • a radial gap is formed, which is subject to considerable changes during operation of the compressor, since on the one hand the blades and the respective shrouds have a different thermal behavior and on the other hand, the blades subject to a change in length due to the centrifugal forces or centrifugal forces acting during operation.
  • the present invention now relates to such details, with the aid of which radial gaps between radially outer ends of blade rings and the respective shroud 17 can be accurately maintained.
  • Fig. 1 are the shrouds 17, which extend between the vane rings 13 and 14 and 15 and 16, connected via curved and resilient walls 19 with a support ring 20, wherein the respective support ring 20 between the respective shroud 17 and the radially outer housing wall 18 is arranged ,
  • the respective shroud 17, the support ring 20 and the between the respective shroud 17 and the respective support ring 20 extending, curved walls 19 each form a bellows-like structure 21, which has a cavity 22.
  • the respective bellows-like structure 21 and thus the cavity 22 surrounds in the circumferential direction completely and thus closed the respective blade ring.
  • the gap between the respective shroud 17 and the radially outer end of the respective blade ring is pneumatically adjustable.
  • the respective radially inner shroud 17 can be pressed radially inward and the respective radially outer support ring 20 radially outward.
  • an opposite deformation of the respective bellows-like structure 21 can be realized.
  • Fig. 1 In the preferred embodiment of Fig. 1 are the curved, elastically yielding walls 19 of the bellows-like structures 21 seen in the axial direction only curved inwardly into the respective cavity 22 into it. In the region of a vertex of the curvature wall sections of the respective wall 19 close a relatively obtuse angle ⁇ of greater than 90 °.
  • Fig. 2 shows a schematic representation of a bellows-like structure 21, described.
  • Fig. 2 shows Fig. 2 in that, in the region of a vertex 29 of the curvature, the wall sections of the respective wall 19 enclose an obtuse angle ⁇ .
  • curved walls 19 are superimposed at an increase in pressure in the corresponding cavity 22 of the respective bellows-like structure 21, two effects.
  • the respective bellows-like structure 21 has a greater radial extent than axial extent.
  • the walls 19 of the respective bellows-type structure 21 have a greater radial extent than axial extent.
  • each bellows-like structures 21 seen in the radial direction have an approximately constant wall thickness.
  • the curved walls 19 seen in the radial direction have a variable wall thickness.
  • each bellows-like structure 21 has a smaller wall thickness than the respective radially outer support ring 20.
  • the support ring 20 of each bellows-like structure 21 is therefore designed with a thicker wall thickness than the respective shroud 17. This is guaranteed in that deformation of the bellows-like structure 21 caused by variation of the pressure prevailing in the respective cavity 22 primarily acts on the shroud 17.
  • Fig. 1 can be further seen that the shroud 17 of each bellows-like structure 21 in a center region seen in the axial direction has a radially outwardly curved, projecting into the respective cavity 22 contour 23.
  • Each bellows-like structure 21 is in each case assigned at least one compressed-air line 24 in order to either introduce compressed air into the respective cavity 22 of the respective bellows-like structure 21 or to discharge it from the same compressed air.
  • a simpler representation shows Fig. 1 such a compressed-air line 24 exclusively for the bellows-like structure 21 positioned in the axial direction between the two guide-blade rings 13 and 14.
  • Each bellows-like structure 21 is assigned at least one such compressed air line 24. The more such compressed air lines 24 per bellows-like structure 21 are present, the faster compressed air can be introduced into the respective cavity 24 or derived from the same.
  • a sensor unit 25 In the embodiment of Fig. 1 is between the two Leitschaufelkränzen 13 and 14 and between the two Leitschaufelkränzen 15 and 16 each a bellows-like structure 21 arranged between the two Leitschaufelkränzen 14 and 15, however, no such bellows-like structure is present. Rather, according to Fig. 1 between the two Leitschaufelkränzen 14 and 15 and thus arranged in the region of a rotor blade ring arranged between the same, a sensor unit 25.
  • the sensor unit 25 With the sensor unit 25, at least the radial dimension of the gap between the corresponding rotor blade ring and the outer ring 17 surrounding this blade ring can be measured. Via a signal line 26, the sensor unit 25 transmits a corresponding actual value to a control device, not shown, wherein the control device compares the actual value with a desired value and depending on the pressure prevailing in the cavities 22 of the bellows structures 21 set pressure such that the actual value approaches the target value ,
  • the compressed air supply into the cavities 22 and the compressed air discharge from the cavities 22 of the bellows-like structures 21 is adjustable via individual valves, so as to adjust the pressure prevailing in the cavities 22 of the two bellows-like structures 21 pressure individually and so each Dimension of the radial gap between the shroud 17 and the corresponding blade ring depending on the respective radial extent of the blade ring individually set.
  • the compressed air supply into the cavities 22 of the bellows-like structures 21 or the Diruck povertyabschreib from the same via a common valve By different radial extensions of the respective blade rings of the compressor 10 required, different deformations of the bellows-like structures 21 are then achieved by an adapted curvature of the curved walls 19 and / or an adapted wall thickness of the curved walls 19 and / or by an adapted radial extent of the bellows-like structures 21 ,
  • the two bellows-like structures 21 are each divided by axially extending parting planes in the axial direction, wherein during manufacture, the two axial halves of the bellows-like structures 21 are welded together. Alternatively, it is also possible to divide the bellows-like structures in the radial direction.
  • Fig. 1 and 2 is in the region of each bellows-like structure 21 each wall 19 seen in the axial direction only curved inwardly into the respective cavity 22 into it.
  • the bellows-type structure 30 according to FIG. 3 has a greater axial extent than radial extent, in particular the walls 19 of the bellows-type structure 30 have a greater axial extent than radial extent.

Abstract

A turbomachine, especially a gas turbine, includes a rotor having rotating blades and a stator having a housing and guide blades. The rotating blades form at least one rotating blade ring, which at one radially outward lying end adjoins an inner ring or casing ring of the housing, thereby defining a gap therebetween. The casing ring is connected to a support ring via curved walls, which together with the casing ring and the support ring bound a cavity and form a bellowslike structure. By changing the pressure prevailing in the cavity of the respective bellowslike structure, the gap between the casing ring and the radially outward lying ends of the respective rotating blade ring can be pneumatically adjusted.

Description

Die Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, nach dem Oberbegriff des Anspruchs 1.The invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1.

Aus der DE 10 2004 037 955 A1 ist eine Turbomaschine mit einem Stator und einem Rotor bekannt, wobei der Rotor Laufschaufeln und der Stator ein Gehäuse und Leitschaufeln aufweist. Die rotorseitigen Laufschaufeln bilden mindestens einen Laufschaufelkranz, der an einem radial außenliegenden Ende an eine radial innenliegende Gehäusewand des Gehäuses angrenzt, von derselben umgeben ist und mit derselben einen radialen Spalt begrenzt. Die radial innenliegende Gehäusewand des Gehäuses wird auch als Innenring bzw. Mantelring bezeichnet und dient insbesondere als Träger für einen Einlaufbelag. Aus der DE 10 2004 037 955 A1 ist weiterhin bekannt, dass der Spalt zwischen dem Mantelring des Gehäuses und dem radial außenliegenden Ende des oder jedes Laufschaufelkranzes zur Bereitstellung eines sogenannten Active Clearance Control über Stelleinrichtungen in seinem Spaltmaß eingestellt bzw. angepasst werden kann, um so automatisch den Spalt zu beeinflussen und über alle Betriebsbedingungen eine optimale Spalthaltung zu gewährleisten. Dabei ist nach der DE 10 2004 037 955 A1 die radial innenliegende Gehäusewand bzw. der Mantelring in Umfangsrichtung segmentiert, wobei vorzugsweise jedem Segment eine separate Stelleinrichtung zugeordnet ist. Die Stelleinrichtungen sind vorzugsweise als elektro-mechanische Aktuatoren ausgeführt.From the DE 10 2004 037 955 A1 For example, a turbomachine including a stator and a rotor is known, wherein the rotor includes rotor blades and the stator includes a housing and vanes. The rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same. The radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining. From the DE 10 2004 037 955 A1 It is also known that the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage. It is after the DE 10 2004 037 955 A1 the radially inner housing wall or the shroud segmented in the circumferential direction, wherein preferably each segment is associated with a separate adjusting device. The adjusting devices are preferably designed as electro-mechanical actuators.

Die DE 101 17 231 A1 offenbart eine Turbomaschine mit einem Stator und einem Rotor, wobei der Spalt zwischen radial außenliegenden Enden der Laufschaufeln und der radial innenliegenden Gehäusewand mit Hilfe einer pneumatischen, also druckluftbetriebenen, Aktuatoreinheit eines Rotorspalt-Steuermoduls eingestellt werden kann. Die pneumatische Aktuatoreinheit des dort offenbarten Rotorspalt-Steuermoduls verfügt über eine Aktuatorkammer, eine Druckkammer und die Aktuatorkammer sowie die Druckkammer verbindende Ventile, wobei abhängig von dem in der Aktuatorkammer herrschenden Druck Dichtelemente des Rotorspalt-Steuermoduls aufgeblasen werden, um so im Sinne eines pneumatischen Active Clearance Control das Spaltmaß des Spalts zwischen radial außenliegenden Enden von Laufschaufeln und dem Mantelring des Gehäuses einzustellen bzw. anzupassen.The DE 101 17 231 A1 discloses a turbomachine with a stator and a rotor, wherein the gap between radially outer ends of the blades and the radially inner housing wall by means of a pneumatic, so compressed air operated, actuator unit of a rotor gap control module can be adjusted. The pneumatic actuator unit of the disclosed therein rotor gap control module has an actuator chamber, a pressure chamber and the actuator chamber and the pressure chamber connecting valves, which are inflated depending on the prevailing pressure in the actuator chamber sealing elements of the rotor gap control module, so in the sense of a pneumatic active clearance Control to adjust or adjust the gap of the gap between radially outer ends of blades and the outer ring of the housing.

Die DE 29 22 835 C2 und die US 5,211,534 offenbaren weitere Turbomaschinen mit einem pneumatischen bzw. druckluftbetriebenen Active Clearance Control.The DE 29 22 835 C2 and the US 5,211,534 reveal further turbomachinery with a pneumatic or pneumatic Active Clearance Control.

So verfügt die Turbomaschine gemäß DE 29 22 835 C2 über einen Stator und einen Rotor, wobei der Spalt zwischen radial außenliegenden Enden der Laufschaufeln und einem Innenring bzw. Mantelring einer Gehäusewand pneumatisch eingestellt werden kann. Hierzu ist der Mantelring über nachgiebige Seitenwände mit einem Stützring verbunden, wobei der Mantelring, der Stützring und die Seitenwände eine faltenbalgartige Struktur bilden. Durch Einstellung des Drucks in einem von der faltenbalgartigen Struktur definierten Hohlraum kann der Spalt zwischen radial außenliegenden Enden der Laufschaufeln und dem Mantelring eingestellt werden. Dabei sind nach der DE 29 22 835 C2 die nachgiebigen Seitenwände mehrfach gewölbt. Die Seitenwände sind nach der DE 29 22 835 C2 demnach in Axialrichtung gesehen abschnittsweise nach innen in den Hohlraum hinein und abschnittsweise nach außen aus dem Hohlraum heraus gewölbt.So has the turbomachine according to DE 29 22 835 C2 via a stator and a rotor, wherein the gap between radially outer ends of the blades and an inner ring or shroud of a housing wall can be adjusted pneumatically. For this purpose, the shroud ring is connected via resilient side walls with a support ring, wherein the shroud, the support ring and the side walls form a bellows-like structure. By adjusting the pressure in a cavity defined by the bellows-type structure, the gap between radially outer ends of the blades and the shroud can be adjusted. Here are after the DE 29 22 835 C2 the flexible side walls arched several times. The side walls are after the DE 29 22 835 C2 Accordingly, seen in the axial direction in sections, inwardly into the cavity and partially outwardly curved out of the cavity.

Das Dokument US-A- 5 344 284 schützt ein pneumatisches Active Clearance Control System mit einem steifen, blechartigen, über den Umfang mehrfach segmentierten Anstreifbelag, wobei jedes Belagsegment über einen separaten, flexiblen, gummiartigen Balg radial beweglich ist. Im Axialschnitt weist der Balg am stromaufwärtigen und stromabwärtigen Ende einfach in den Hohlraum des Balges hinein gewölbte Wände auf. Vom Scheitelpunkt der Wölbung bis zum radial inneren Ende der Balgwand ist eine abdichtende Überlappung der Balgwand mit einem radial nach Außen vorstehenden Rand des steifen Anstreifbelags vorhanden. In diesem Bereich ist die Balgwand in axialer Richtung nach Außen nicht oder nur stark eingeschränkt beweglich. Die Struktur nach us-A-5344284 ist ein sogenannter verbund bestehend aus balgen und mantelring ohne verbindung zu benochbarten leitschautelkränzen.The document US-A-5,344,284 protects a pneumatic Active Clearance Control System with a rigid, sheet-like, circumferentially multi-segmented squelch, with each pad segment radially movable via a separate, flexible, rubber-like bellows. In axial section, the bellows at the upstream and downstream end simply in the cavity of the bellows in curved walls. From the vertex of the curvature to the radially inner end of the bellows wall, a sealing overlap of the bellows wall with a radially outwardly projecting edge of the rigid Anstreifbelags is present. In this area, the bellows wall in the axial direction to the outside is not or only very limited mobility. The structure according to US-A-5344284 is a so-called composite consisting of bellows and shell ring without connection to benochbarten Leitschautelkränzen.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Turbomaschine mit einem pneumatischen Active Clearance Control zu schaffen.On this basis, the present invention is based on the problem to provide a novel turbomachine with a pneumatic Active Clearance Control.

Dieses Problem wird durch eine Turbomaschine gemäß Anspruch 1 gelöst. In bekannter Weise ist im Bereich der oder jeder faltenbalgartigen Struktur jede den Mantelring mit dem Stützring verbindende Wand in Axialrichtung gesehen ausschließlich einfach nach innen in den jeweiligen Hohlraum hinein gewölbt. Erfindungsgemäß ist jede gewölbte Wand nach Art eines Kniehebels ausgeführt, wobei die Wandabschnitte einen stumpfen Winkel von größer als 90° einschließen und zur Aufnahme von Druckkräften geeignet sind.This problem is solved by a turbomachine according to claim 1. In a known manner, in the region of the or each bellows-like structure, each wall connecting the jacket ring to the support ring is, seen in the axial direction, exclusively inwardly inward arched into the respective cavity. According to the invention, each curved wall is designed in the manner of a toggle lever, wherein the wall sections include an obtuse angle greater than 90 ° and are suitable for receiving pressure forces.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteramprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
einen Querschnitt durch statorseitige Baugruppen einer erfindungsgemäßen Turbomaschine; und
Fig. 2
eine schematisierte Darstellung einer faltenbalgartigen Struktur der Turboma- schine gemäß Fig. 1.
Preferred developments of the invention will become apparent from the Unteramprüchen and the following description. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a cross section through stator-side modules of a turbomachine according to the invention; and
Fig. 2
a schematic representation of a bellows-like structure of the turbomachine according to Fig. 1 ,

Fig. 1 zeigt einen ausschnittweisen Querschnitt durch einen Stator eines Verdichters 10 einer Turbomaschine, wobei der Stator ein Gehäuse 11 sowie mehrere feststehende Leitschaufeln 12 umfasst. Die statorseitigen Leitschaufeln 12 bilden sogenannte Leitschaufelkränze, die in Axialrichtung gesehen hintereinander angeordnet sind. In Fig. 1 sind insgesamt vier feststehende, statorseitige Leitschaufelkränze 13, 14, 15 und 16 gezeigt. Fig. 1 shows a partial cross-section through a stator of a compressor 10 of a turbomachine, wherein the stator comprises a housing 11 and a plurality of stationary vanes 12. The stator-side guide vanes 12 form so-called vane rings which, viewed in the axial direction, are arranged one behind the other. In Fig. 1 a total of four fixed, stator vane rings 13, 14, 15 and 16 are shown.

Neben dem Stator umfasst der Verdichter 10 einen in Fig. 1 nicht dargestellten Rotor, wobei der Rotor von mehreren in axialer Richtung hintereinander angeordneten, nicht dargestellten Rotorscheiben gebildet ist, wobei jede Rotorscheibe in Umfangsrichtung nebeneinander mehrere, ebenfalls nicht dargestellte Laufschaufeln trägt. Die einer Rotorscheibe zugeordneten, in Umfangsrichtung nebeneinander angeordneten Laufschaufeln bilden sogenannte Laufschaufelkränze, wobei zwischen jeweils zwei benachbarten Leitschaufelkränzen 13 und 14, 14 und 15 sowie 15 und 16 jeweils ein nicht dargestellter Laufschaufelkranz angeordnet ist.In addition to the stator, the compressor 10 comprises an in Fig. 1 Rotor, not shown, wherein the rotor of a plurality of axially arranged behind the other, not shown rotor disks is formed, each rotor disk in the circumferential direction next to each other several, also not shown blades carries. The rotor blades associated, circumferentially juxtaposed blades form so-called blade rings, wherein between each two adjacent vane rings 13 and 14, 14 and 15 and 15 and 16 are each a non-illustrated blade ring is arranged.

Das Gehäuse 11 des Stators des Verdichters 10 umfasst eine radial innenliegende Gehäusewand, wobei die radial innenliegende Gehäusewand im Bereich jedes rotorseitigen, in Fig. 1 nicht gezeigten Laufschaufelkranzes einen sogenannten Innenring bzw. Mantelring 17 bildet und den jeweiligen Laufschaufelkranz radial außen umschließt. Neben den Mantelringen 17 der radial innenliegenden Gehäusewand umfasst das Gehäuse 11 weiterhin eine radial außenliegende Gehäusewand 18.The housing 11 of the stator of the compressor 10 comprises a radially inner housing wall, wherein the radially inner housing wall in the region of each rotor-side, in Fig. 1 not shown blade ring forms a so-called inner ring or shroud 17 and surrounds the respective blade ring radially on the outside. Next to the jacket rings 17 of the radially inner housing wall, the housing 11 further comprises a radially outer housing wall 18th

Wie bereits ausgeführt, bildet die radial innenliegende Gehäusewand im Bereich jedes nicht-dargestellten, rotorseitigen Laufschaufelkranzes einen sogenannten Mantelring 17, der den Laufschaufelkranz radial außen umschließt. Zwischen den radial außenliegenden Enden der Laufschaufeln eines jeden Laufschaufelkranzes und dem jeweiligen Mantelring 17 ist dabei ein radialer Spalt ausgebildet, der während des Betriebs des Verdichters erheblichen Veränderungen unterliegt, da einerseits die Laufschaufeln und die jeweiligen Mantelringe ein unterschiedliches thermisches Verhalten aufweisen und da andererseits die Laufschaufeln aufgrund der im Betrieb wirkenden Fliehkräfte bzw. Zentrifugalkräfte einer Längenänderung unterliegen.As already stated, forms the radially inner housing wall in the region of each non-illustrated, rotor-side blade ring a so-called shroud ring 17 which surrounds the blade ring radially outward. Between the radially outer ends of the blades of each blade ring and the respective shroud 17, a radial gap is formed, which is subject to considerable changes during operation of the compressor, since on the one hand the blades and the respective shrouds have a different thermal behavior and on the other hand, the blades subject to a change in length due to the centrifugal forces or centrifugal forces acting during operation.

Die Einhaltung definierter Abmessungen des jeweiligen Spalts zwischen den radial außenliegenden Enden der Laufschaufeln eines Laufschaufelkranzes und dem jeweiligen Mantelring 17 bereitet während des Betriebs erhebliche Schwierigkeiten, ist jedoch zur Optimierung des Wirkungsgrads von entscheidender Bedeutung.Compliance with defined dimensions of the respective gap between the radially outer ends of the blades of a blade ring and the respective shroud 17 prepares during operation considerable difficulties, however, is to optimize the efficiency of crucial importance.

Die hier vorliegende Erfindung betrifft nun solche Details, mit Hilfe derer radiale Spalte zwischen radial außenliegenden Enden von Laufschaufelkränzen und dem jeweiligen Mantelring 17 exakt eingehalten werden können.The present invention now relates to such details, with the aid of which radial gaps between radially outer ends of blade rings and the respective shroud 17 can be accurately maintained.

Gemäß Fig. 1 sind die Mantelringe 17, die sich zwischen den Leitschaufelkränzen 13 und 14 sowie 15 und 16 erstrecken, über gewölbte sowie elastisch nachgiebige Wände 19 mit einem Stützring 20 verbunden, wobei der jeweilige Stützring 20 zwischen dem jeweiligen Mantelring 17 und der radial außenliegenden Gehäusewand 18 angeordnet ist. Der jeweilige Mantelring 17, der Stützring 20 sowie die sich zwischen den jeweiligen Mantelring 17 und dem jeweiligen Stützring 20 erstreckenden, gewölbten Wände 19 bilden jeweils eine faltenbalgähnliche Struktur 21, die einen Hohlraum 22 aufweist. Die jeweilige faltenbalgähnliche Struktur 21 und damit der Hohlraum 22 umgibt in Umfangsrichtung gesehen vollständig und damit geschlossen den jeweiligen Laufschaufelkranz.According to Fig. 1 are the shrouds 17, which extend between the vane rings 13 and 14 and 15 and 16, connected via curved and resilient walls 19 with a support ring 20, wherein the respective support ring 20 between the respective shroud 17 and the radially outer housing wall 18 is arranged , The respective shroud 17, the support ring 20 and the between the respective shroud 17 and the respective support ring 20 extending, curved walls 19 each form a bellows-like structure 21, which has a cavity 22. The respective bellows-like structure 21 and thus the cavity 22 surrounds in the circumferential direction completely and thus closed the respective blade ring.

Durch Veränderung eines im jeweiligen Hohlraum 22 der faltenbalgähnlichen Struktur 21 herrschenden Drucks ist der Spalt zwischen dem jeweiligen Mantelring 17 und dem radial außenliegenden Ende des jeweiligen Laufschaufelkranzes pneumatisch einstellbar. Bei einer Druckerhöhung im Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 kann der jeweilige, radial innenliegende Mantelring 17 nach radial innen und der jeweilige, radial außenliegende Stützring 20 nach radial außen gedrückt werden. Durch eine Druckreduzierung im Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 kann eine entgegengesetzte Verformung der jeweiligen faltenbalgähnlichen Struktur 21 realisiert werden.By changing a prevailing in the respective cavity 22 of the bellows-like structure 21 pressure, the gap between the respective shroud 17 and the radially outer end of the respective blade ring is pneumatically adjustable. With an increase in pressure in the cavity 22 of the respective bellows-like structure 21, the respective radially inner shroud 17 can be pressed radially inward and the respective radially outer support ring 20 radially outward. By reducing the pressure in the cavity 22 of the respective bellows-like structure 21, an opposite deformation of the respective bellows-like structure 21 can be realized.

Im bevorzugten Ausführungsbeispiel der Fig. 1 sind die gewölbten, elastisch nachgiebigen Wände 19 der faltenbalgähnlichen Strukturen 21 in Axialrichtung gesehen ausschließlich einfach nach innen in den jeweiligen Hohlraum 22 hinein gewölbt. Im Bereich eines Scheitelpunkts der Wölbung schließen Wandabschnitte der jeweiligen Wand 19 einen relativ stumpfen Winkel α von größer als 90° ein. Dies wird nachfolgend unter Bezugnahme auf Fig. 2, die eine schematisierte Darstellung einer faltenbalgähnlichen Struktur 21 zeigt, beschrieben.In the preferred embodiment of Fig. 1 are the curved, elastically yielding walls 19 of the bellows-like structures 21 seen in the axial direction only curved inwardly into the respective cavity 22 into it. In the region of a vertex of the curvature wall sections of the respective wall 19 close a relatively obtuse angle α of greater than 90 °. This will be explained below with reference to Fig. 2 , which shows a schematic representation of a bellows-like structure 21, described.

So zeigt Fig. 2, dass im Bereich eines Scheitelpunkts 29 der Wölbung die Wandabschnitte der jeweiligen Wand 19 einen stumpfen Winkel α einschließen. Bei derart gewölbten Wänden 19 überlagern sich bei einer Druckerhöhung im entsprechenden Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 zwei Effekte.So shows Fig. 2 in that, in the region of a vertex 29 of the curvature, the wall sections of the respective wall 19 enclose an obtuse angle α. In such curved walls 19 are superimposed at an increase in pressure in the corresponding cavity 22 of the respective bellows-like structure 21, two effects.

Erstens werden bedingt durch die Druckerhöhung im Hohlraum 22 der jeweilige Mantelring 17 sowie der jeweilige Stützring 20 unmittelbar in Radialrichtung gesehen auseinander gedrückt. Zweitens wird dieses radiale Auseinanderdrücken des jeweiligen Mantelrings 17 und Stützrings 20 durch einen kniehebelartigen Effekt der gewölbten Wände 19 unterstützt bzw. zumindest nicht behindert. Dabei sind die gewölbten Wände 19 im Wesentlichen ausschließlich Druckkräften ausgesetzt.First, due to the pressure increase in the cavity 22, the respective shroud 17 and the respective support ring 20 are pressed apart as viewed directly in the radial direction. Second, this radial disengagement of the respective shroud 17 and support ring 20 is supported by a toggle-like effect of the curved walls 19 or at least not hindered. The curved walls 19 are exposed to essentially exclusively compressive forces.

Gemäß Fig. 1 und 2 weist die jeweilige faltenbalgartige Struktur 21 eine größere Radialerstreckung als Axialerstreckung auf. Vorzugsweise weisen die Wände 19 der jeweiligen faltenbalgartigen Struktur 21 eine größere Radialerstreckung als Axialerstreckung aufweisen.According to Fig. 1 and 2 the respective bellows-like structure 21 has a greater radial extent than axial extent. Preferably, the walls 19 of the respective bellows-type structure 21 have a greater radial extent than axial extent.

Im gezeigten Ausführungsbeispiel der Fig. 1 verfügen die gewölbten Wände 19 jeder faltenbalgähnlichen Strukturen 21 in Radialrichtung gesehen über eine in etwa konstante Wandstärke. Im Unterschied hierzu ist es auch möglich, dass die gewölbten Wände 19 in Radialrichtung gesehen eine veränderliche Wandstärke aufweisen.In the illustrated embodiment of the Fig. 1 The arched walls 19 of each bellows-like structures 21 seen in the radial direction have an approximately constant wall thickness. In contrast, it is also possible that the curved walls 19 seen in the radial direction have a variable wall thickness.

Wie ebenfalls Fig. 1 entnommen werden kann, weist der radial innenliegende Mantelring 17 jeder faltenbalgähnlichen Struktur 21 eine geringere Wandstärke auf als der jeweilige radial außenliegende Stützring 20. Der Stützring 20 einer jeden faltenbalgähnlichen Struktur 21 ist demnach mit einer dickeren Wandstärke ausgeführt als der jeweilige Mantelring 17. Hierdurch wird gewährleistet, dass durch Veränderung des im jeweiligen Hohlraum 22 herrschenden Drucks bewirkte Verformungen der faltenbalgähnlichen Struktur 21 in erster Linie auf den Mantelring 17 wirken.Like also Fig. 1 can be removed, the radially inner shroud 17 each bellows-like structure 21 has a smaller wall thickness than the respective radially outer support ring 20. The support ring 20 of each bellows-like structure 21 is therefore designed with a thicker wall thickness than the respective shroud 17. This is guaranteed in that deformation of the bellows-like structure 21 caused by variation of the pressure prevailing in the respective cavity 22 primarily acts on the shroud 17.

Fig. 1 kann weiterhin entnommen werden, dass der Mantelring 17 einer jeden faltenbalgähnlichen Struktur 21 in einem in Axialrichtung gesehen mittleren Bereich eine nach radial außen gewölbte, in den jeweiligen Hohlraum 22 hineinragende Kontur 23 aufweist. Fig. 1 can be further seen that the shroud 17 of each bellows-like structure 21 in a center region seen in the axial direction has a radially outwardly curved, projecting into the respective cavity 22 contour 23.

Hierdurch wird erzielt, dass bei einer Verformung des Mantelrings 17 infolge einer Druckänderung im Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 eine äußere Kontur 28 des Mantelrings 17 in Radialrichtung gesehen im Wesentlichen ausschließlich parallel verschoben wird, so dass ein Spalt zwischen dem Mantelring 17 und dem Laufschaufelkranz exakt eingestellt werden kann.As a result, it is achieved that upon deformation of the shroud 17 as a result of a pressure change in the cavity 22 of the respective bellows-like structure 21, an outer contour 28 of the shroud 17 is substantially exclusively displaced in parallel, so that a gap between the shroud 17 and the blade ring can be set exactly.

Jeder faltenbalgähnlichen Struktur 21 ist jeweils mindestens eine Druckluftleitung 24 zugeordnet, um in den jeweiligen Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 entweder Druckluft einzuleiten bzw. aus demselben Druckluft abzuleiten. Aus Gründen einer einfacheren Darstellung zeigt Fig. 1 eine derartige Druckluftleitung 24 ausschließlich für die in Axialrichtung gesehen zwischen den beiden Leitschaufelkränzen 13 und 14 positionierte faltenbalgähnliche Struktur 21. Jeder faltenbalgähnlichen Struktur 21 ist mindestens eine derartige Druckluftleitungen 24 zugeordnet. Je mehr derartige Druckluftleitungen 24 pro faltenbalgähnlicher Struktur 21 vorhanden sind, desto schneller kann Druckluft in den jeweiligen Hohlraum 24 eingeleitet bzw. aus demselben abgeleitet werden.Each bellows-like structure 21 is in each case assigned at least one compressed-air line 24 in order to either introduce compressed air into the respective cavity 22 of the respective bellows-like structure 21 or to discharge it from the same compressed air. For reasons a simpler representation shows Fig. 1 such a compressed-air line 24 exclusively for the bellows-like structure 21 positioned in the axial direction between the two guide-blade rings 13 and 14. Each bellows-like structure 21 is assigned at least one such compressed air line 24. The more such compressed air lines 24 per bellows-like structure 21 are present, the faster compressed air can be introduced into the respective cavity 24 or derived from the same.

Im Ausführungsbeispiel der Fig. 1 ist zwischen den beiden Leitschaufelkränzen 13 und 14 sowie zwischen den beiden Leitschaufelkränzen 15 und 16 jeweils eine faltenbalgähnliche Struktur 21 angeordnet, zwischen den beiden Leitschaufelkränzen 14 und 15 ist hingegen keine derartige faltenbalgähnliche Struktur vorhanden. Vielmehr ist gemäß Fig. 1 zwischen den beiden Leitschaufelkränzen 14 und 15 und damit im Bereich eines zwischen denselben angeordneten Laufschaufelkranzes eine Sensoreinheit 25 angeordnet.In the embodiment of Fig. 1 is between the two Leitschaufelkränzen 13 and 14 and between the two Leitschaufelkränzen 15 and 16 each a bellows-like structure 21 arranged between the two Leitschaufelkränzen 14 and 15, however, no such bellows-like structure is present. Rather, according to Fig. 1 between the two Leitschaufelkränzen 14 and 15 and thus arranged in the region of a rotor blade ring arranged between the same, a sensor unit 25.

Mit der Sensoreinheit 25 kann zumindest die radiale Abmessung des Spalts zwischen dem entsprechenden Läufschaufelkranz und dem diesen Laufschaufelkranz umgebenden Mantelring 17 vermessen werden. Über eine Signalleitung 26 übermittelt die Sensoreinheit 25 einen entsprechenden Istwert an eine nicht dargestellte Regeleinrichtung, wobei die Regeleinrichtung den Istwert mit einem Sollwert vergleicht und abhängig hiervon den in den Hohlräumen 22 der faltenbalgartigen Strukturen 21 herrschenden Druck derart einstellt, dass sich der Istwert dem Sollwert annähert.With the sensor unit 25, at least the radial dimension of the gap between the corresponding rotor blade ring and the outer ring 17 surrounding this blade ring can be measured. Via a signal line 26, the sensor unit 25 transmits a corresponding actual value to a control device, not shown, wherein the control device compares the actual value with a desired value and depending on the pressure prevailing in the cavities 22 of the bellows structures 21 set pressure such that the actual value approaches the target value ,

Dabei kann vorgesehen sein, dass die Druckluftzufuhr in die Hohlräume 22 bzw. die Druckluftabfuhr aus den Hohlräumen 22 der faltenbalgartigen Strukturen 21 über individuelle Ventile einstellbar ist, um so den in den Hohlräumen 22 der beiden faltenbalgartigen Strukturen 21 herrschenden Druck individuell einzustellen und so jeweils die Abmessung des radialen Spalts zwischen dem Mantelring 17 und dem entsprechenden Laufschaufelkranz anhängig von der jeweiligen Radialerstreckung des Laufschaufelkranzes individuell einzustellen.It can be provided that the compressed air supply into the cavities 22 and the compressed air discharge from the cavities 22 of the bellows-like structures 21 is adjustable via individual valves, so as to adjust the pressure prevailing in the cavities 22 of the two bellows-like structures 21 pressure individually and so each Dimension of the radial gap between the shroud 17 and the corresponding blade ring depending on the respective radial extent of the blade ring individually set.

Alternativ kann vorgesehen sein, die Druckluftzufuhr in die Hohlräume 22 der faltenbalgartigen Strukturen 21 bzw. die Diruckluftabfuhr aus denselben über ein gemeinsames Ventil einzustellen. Durch unterschiedliche Radialerstreckungen der jeweiligen Laufschaufelkränze des Verdichters 10 erforderliche, unterschiedliche Verformungen der faltenbalgähnlichen Strukturen 21 sind dann durch eine angepasste Wölbung der gewölbten Wände 19 und/oder eine angepasste Wandstärke der gewölbten Wände 19 und/oder durch eine angepasste radiale Erstreckung der faltenbalgähnlichen Strukturen 21 erzielbar.Alternatively, it may be provided that the compressed air supply into the cavities 22 of the bellows-like structures 21 or the Diruckluftabfuhr from the same via a common valve. By different radial extensions of the respective blade rings of the compressor 10 required, different deformations of the bellows-like structures 21 are then achieved by an adapted curvature of the curved walls 19 and / or an adapted wall thickness of the curved walls 19 and / or by an adapted radial extent of the bellows-like structures 21 ,

Gemäß Fig. 1 sind die beiden faltenbalgähnlichen Strukturen 21 jeweils durch sich in Radialrichtung erstreckende Trennebenen in Axialrichtung geteilt, wobei bei der Fertigung die beiden Axialhälften der faltenbalgähnlichen Strukturen 21 miteinander verschweißt werden. Alternativ ist es auch möglich, die faltenbalgähnlichen Strukturen in Radialrichtung zu teilen.According to Fig. 1 the two bellows-like structures 21 are each divided by axially extending parting planes in the axial direction, wherein during manufacture, the two axial halves of the bellows-like structures 21 are welded together. Alternatively, it is also possible to divide the bellows-like structures in the radial direction.

Gemäß Fig. 1 und 2 ist im Bereich jeder faltenbalgartigen Struktur 21 jede Wand 19 in Axialrichtung gesehen ausschließlich einfach nach innen in den jeweiligen Hohlraum 22 hinein gewölbt.According to Fig. 1 and 2 is in the region of each bellows-like structure 21 each wall 19 seen in the axial direction only curved inwardly into the respective cavity 22 into it.

Die faltenbalgartige Struktur 30 gemäß Fig. 3 weist eine größere Axialerstreckung als Radialerstreckung auf, insbesondere weisen die Wände 19 der faltenbalgartigen Struktur 30 eine größere Axialerstreckung als Radialerstreckung auf.The bellows-type structure 30 according to FIG. 3 has a greater axial extent than radial extent, in particular the walls 19 of the bellows-type structure 30 have a greater axial extent than radial extent.

Claims (9)

  1. A turbo-engine having a stator and a rotor, wherein the rotor has rotor blades and the stator has a housing (11) and guide vanes (12), wherein the rotor blades on the rotor side form at least one rotor-blade ring, wherein the or each rotor-blade ring at a radially external end adjoins an inner ring or jacket ring (17) of the housing (11) on the stator side, is surrounded by the same and delimits a gap with the same, wherein the respective jacket ring (17) is connected to a support ring (20) by way of curved walls (19) which together with the jacket ring (17) and the support ring (20) delimit a cavity (22) and form a bellows-like structure (21), wherein by changing a pressure that prevails in the cavity (22) of the respective bellows-like structure (21) it is possible to adjust pneumatically the gap between the jacket ring (17) and the radially external end of the respective rotor-blade ring, and wherein in the region of the or each bellows-like structure (21) each wall (19), viewed in the axial direction, is curved only once inwards into the respective cavity (22), wherein each wall (19) is constructed in the manner of a toggle lever against action of an excess pressure with respect to the environment, wherein in the region of a vertex (29) of the curvature wall sections of the respective wall (19) enclose an obtuse angle of more than 90°, and wherein the wall sections are suitable for taking up pressure forces,
    characterised in that
    the jacket ring (17) together with the support ring (20) and the curved walls (19) present, in an axial-radial section, an integral formation which is connected to a guide-vane ring in a form-locking manner on at least one side in the region of the jacket ring.
  2. A turbo-engine according to claim 1,
    characterised in that
    the walls (19) have a constant wall thickness.
  3. A turbo-engine according to claim 1,
    characterised in that
    the walls have a variable wall thickness, viewed in the radial direction.
  4. A turbo-engine according to one of claims 1 to 3,
    characterised in that
    in the region of the or each bellows-like structure (21) the jacket ring (17) has a smaller wall thickness than the support ring (20).
  5. A turbo-engine according to one of claims 1 to 4,
    characterised in that
    in the region of the or each bellows-like structure (21) the jacket ring (17) has in a central region, viewed in the axial direction, a contour (23) that is curved into the cavity (22).
  6. A turbo-engine according to one of claims 1 to 5,
    characterised in that
    associated with the or each bellows-like structure there is in each case at least one compressed-air line (24) in order to introduce compressed air into the respective cavity (22) or to divert it out of the cavity.
  7. A turbo-engine according to one of claims 1 to 6,
    characterised in that
    associated with at least two rotor-blade rings there is a respective bellows-like structure (21), and in that arranged between the two rotor-blade rings, with which a respective bellows-like structure (21) is associated, there is at least one rotor-blade ring with which a sensor unit (25) is associated, wherein the or each sensor unit (25) measures the radial dimension of the gap in the region of the respective rotor-blade ring and transmits a corresponding actual value to a regulating device, and wherein the regulating device compares the actual value with a desired value and as a function thereof adjusts the pressure that prevails in the cavities (22) of the respective bellows-like structures (21) in such a way that the actual value approximates the desired value.
  8. A turbo-engine according to claim 7,
    characterised in that
    the compressed-air supply into the cavities (22) or the compressed-air removal from the cavities (22) can be adjusted by way of a common valve, wherein, as a result of differing radial extents of the respective rotor-blade rings, necessary different deformations of the bellows-like structures (21) can be attained by means of an adapted curvature and/or adapted wall thickness of the curved walls of the respective bellows-like structures (21).
  9. A turbo-engine according to claim 7,
    characterised in that
    the compressed-air supply into the cavities (22) or the compressed-air removal from the cavities (22) can be adjusted by way of individual valves, wherein, as a result of differing radial extents of the respective rotor-blade rings, necessary different deformations of the bellows-like structures (21) can be attained by means of an individual compressed-air supply or compressed-air removal.
EP07846281A 2006-11-09 2007-10-30 Turbo engine Not-in-force EP2087208B9 (en)

Applications Claiming Priority (2)

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DE102006052786A DE102006052786B4 (en) 2006-11-09 2006-11-09 turbomachinery
PCT/DE2007/001946 WO2008055474A1 (en) 2006-11-09 2007-10-30 Turbo engine

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EP2087208A1 EP2087208A1 (en) 2009-08-12
EP2087208B1 true EP2087208B1 (en) 2011-01-26
EP2087208B9 EP2087208B9 (en) 2012-04-25

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AT (1) ATE497088T1 (en)
CA (1) CA2666200A1 (en)
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WO (1) WO2008055474A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218880A1 (en) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Active clearance control for gas turbines
FR3024492B1 (en) * 2014-07-29 2019-08-23 Safran Aircraft Engines ELEMENT COMPRISING A STATOR AND A TURBOMACHINE ROTOR WITH A SEAL AND TESTING THIS SEAL
US10794213B2 (en) * 2016-06-21 2020-10-06 Rolls-Royce North American Technologies Inc. Blade tip clearance control for an axial compressor with radially outer annulus
US10851712B2 (en) 2017-06-27 2020-12-01 General Electric Company Clearance control device

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2922835C2 (en) 1979-06-06 1985-06-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Circumferential gap seal on axial flow machines
US4329114A (en) * 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
JPS5741407A (en) * 1980-08-22 1982-03-08 Hitachi Ltd Sealing mechanism on top of turbine rotor blade
GB2103294B (en) * 1981-07-11 1984-08-30 Rolls Royce Shroud assembly for a gas turbine engine
JPS5820904A (en) 1981-07-29 1983-02-07 Hitachi Ltd Seal structure of tip of moving blade for gas turbine
GB2169962B (en) * 1985-01-22 1988-07-13 Rolls Royce Blade tip clearance control
JPS62142808A (en) * 1985-12-18 1987-06-26 Toshiba Corp Clearance control device for gas turbine
US4784569A (en) * 1986-01-10 1988-11-15 General Electric Company Shroud means for turbine rotor blade tip clearance control
GB2195715B (en) * 1986-10-08 1990-10-10 Rolls Royce Plc Gas turbine engine rotor blade clearance control
DE3830762C2 (en) * 1988-09-09 1994-08-18 Mtu Muenchen Gmbh Device for holding a jacket ring in gas turbines
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
US4971517A (en) * 1988-12-27 1990-11-20 Allied-Signal Inc. Turbine blade clearance controller
GB9103809D0 (en) * 1991-02-23 1991-04-10 Rolls Royce Plc Blade tip clearance control apparatus
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
DE10117231A1 (en) 2001-04-06 2002-10-31 Hodson Howard Rotor gap control module
US6918743B2 (en) * 2002-10-23 2005-07-19 Pratt & Whitney Canada Ccorp. Sheet metal turbine or compressor static shroud
DE102004037955A1 (en) 2004-08-05 2006-03-16 Mtu Aero Engines Gmbh Turbomachine, in particular gas turbine

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ATE497088T1 (en) 2011-02-15
DE102006052786A1 (en) 2008-05-15
US20100003122A1 (en) 2010-01-07
DE102006052786B4 (en) 2011-06-30
US8608435B2 (en) 2013-12-17
EP2087208B9 (en) 2012-04-25
WO2008055474A1 (en) 2008-05-15
EP2087208A1 (en) 2009-08-12
CA2666200A1 (en) 2008-05-15

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